JP6949594B2 - Systems and methods for fast detection of surface and subsurface FOD and defects - Google Patents

Description

The present disclosure relates generally to systems and methods for fast detection of foreign object debris and defects on the surface and subsurface, more specifically during the process of composite layup. And systems and methods for fast detection of foreign matter and defects under the surface.

Composites generally have a high strength-to-weight ratio by nature, so more and more composites replace traditional materials such as aluminum alloys and alloy steels with different structural members. It is used in. In general, a composite material is composed of reinforcing fibers having a network structure that is generally layered on top of each other and a polymer resin, and the polymer resin sufficiently wets the reinforcing fibers and tightly bonds the resin and the reinforcing fibers. I'm letting you. High-speed composite layup machines are typically used to form each layer, and such layup machines can stack composites at a rate of 3000 inches / minute.

However, the presence of foreign object debris (FOD), contamination, or other types of tape layup anomalies on the surface or inside of the formed composite part in its pre-cured state can cause problems. For example, even small amounts of moisture or other types of contaminants that are trapped or attached to the surface can cause delamination and porosity in the cured composite. In addition, debris such as bagging material, Teflon® tape, or small pieces of breathing material used in composite layups are enclosed in the composite layer. Delamination, air bubbles and wrinkles can occur in composite parts. During the manufacture of composite parts made of laminated carbon fiber reinforced polymer (CFRP) tapes, a type of FOD called fuzzball occurs. So-called "thread threads" are formed of strands of CFRP tape that are rubbed in contact with the spool holding the tape and can accidentally fall onto the surface of the composite part being manufactured. In addition, other types of layup anomalies such as twists, folds, untacked tows, wrinkles and bridging occur during the layup process. However, at present, FOD and defect detection are performed manually and visually. However, it is often difficult to detect visually because the FOD and defects are transparent and the color of the surface of the composite material is easily mixed. Thus, manually detecting FOD and defects is a time consuming and unreliable method. In particular, large and expensive composite parts can fail non-destructive inspection if FOD materials and defects are not detected and removed or repaired prior to curing.

Currently, integrated composite parts are used in many applications, including parts for commercial aircraft, but the cost of manufacturing such parts is very high. If very small FOD substances, contaminants or defects are left in the stacking stage of such parts, manufacturing defects can occur, requiring repair of the parts and, in some cases, failing inspections. .. Repairs or rejects of such parts can be very costly, lead to schedule delays and inventory problems.

Therefore, there is a need for a system that automatically and quickly inspects surface and subsurface FOD, contamination and defects during the high speed composite layup process.

In the first aspect, a system for detecting foreign matter or defects on and / or under the surface is disclosed. The system includes members configured to move above the surface. In addition, the system includes a thermal excitation source fixed to the member and configured to induce infrared rays on the surface. Further, the system includes an infrared camera fixed to the member at a predetermined distance from the thermal excitation source. The infrared camera is configured to scan the surface as the member moves above the surface to detect and output scan information about the surface. Finally, the system includes the thermal excitation source and a controller connected to the infrared camera. The controller is configured to process the scan information from the infrared camera to identify foreign objects or defects located on and / or below the surface.

In additional embodiments, the system may include terminals connected to the controller. The terminal has a display. The controller can be further configured to display on the display upon identifying a foreign object or defect located on and / or below the surface.

In the second additional embodiment, the surface may be the outer layer of the composite part formed by the composite layup machine. The composite layup machine has a head attached to a first gantry for moving above the composite during the formation of the composite. The member is a second gantry for moving separately above the composite part during formation. In addition, the controller can be configured to detect defects in the composite component, including twists, breaks, poor toe adhesion, wrinkles or bridging. In addition, the controller can be configured to measure layer-to-layer overlap and gaps in the composite material in real time.

In a third additional embodiment, the surface may be the outer layer of the composite component formed by the composite layup machine. The composite layup machine has a head attached to a first gantry for moving above the composite during the formation of the composite. The member may correspond to the first gantry. Further, the infrared camera may be a radiation analysis infrared camera. Further, the controller can be configured to provide temperature information for the upper layer and the lower surface of the composite component based on the scan information output from the radioimmunoassay infrared camera. In addition, the controller can be configured to detect defects in the composite component, including twists, breaks, poor toe adhesion, wrinkles or bridging. Finally, the controller can be configured to measure layer-to-layer overlap and gaps in the composite material in real time.

In a fourth additional embodiment, the surface may be the outer layer of a composite part formed by a composite layup machine using carbon fiber reinforced polymer tape. When the carbon fiber reinforced polymer tape comes into contact with the spool, the carbon fiber reinforced polymer tape is rubbed during operation to form a thread of carbon fiber reinforced polymer that accidentally falls on the surface. The controller can be configured to process the scan information from the infrared camera to detect a thread of carbon fiber reinforced polymer on the surface of the component.

In the second aspect, a system for detecting foreign matter or defects on and / or under the surface is disclosed. The system includes members fixed above the movable surface. The system also includes a thermal excitation source that is fixed to the member and that induces infrared rays to the surface. The system is an infrared camera fixed to the member, which scans the surface as the surface moves below the member to detect and output scan information about the surface. Includes an infrared camera configured to. Finally, the system includes the thermal excitation source and a controller connected to the infrared camera. The controller is configured to process the scan information from the infrared camera to identify foreign objects or defects located on and / or below the surface.

In an additional embodiment, the system may include a terminal connected to the controller and having a display. The controller can be further configured to display on the display upon identifying a foreign object or defect or internal defect located on and / or below the surface.

In yet another additional embodiment, the surface is an outer layer of composite parts formed by a composite layup machine. The composite layup machine has a head attached to the gantry. The composite part moves below the gantry during the formation of the composite part. The member corresponds to the gantry. The infrared camera may be a radiation analysis infrared camera, and the controller is configured to provide upper layer and subsurface temperature information in the composite component based on scan information output from the radiation analysis infrared camera. can do.

In yet another additional embodiment, the controller can be configured to detect defects in the composite component, including twists, breaks, poor toe adhesion, wrinkles or bridging. In addition, the controller can be configured to measure layer-to-layer overlap and gaps in the composite material in real time.

In yet another additional embodiment, the surface is an outer layer of composite parts formed by a composite layup machine using carbon fiber reinforced polymer tape. When the carbon fiber reinforced polymer tape comes into contact with the spool, the carbon fiber reinforced polymer tape is rubbed during operation to form a thread of carbon fiber reinforced polymer that accidentally falls on the surface. The controller can be configured to process the scan information from the infrared camera to detect a thread of carbon fiber reinforced polymer on the surface.

In the third aspect, a method for detecting foreign matter or defects on and / or under the surface of the work is disclosed. An infrared beam from an infrared excitation source is guided to the surface of the work. The surface of the work is scanned by an infrared camera, and scan information about the surface of the work is detected and output. The scan information from the infrared camera is processed to identify foreign objects or defects located on and / or below the surface of the work. In an additional embodiment, the infrared camera is a radiation analysis infrared camera, the scan information from the infrared camera is processed to provide temperature information for the upper and lower layers of the work.

The features, functions and effects described above can be individually realized in various embodiments, but may be combined with each other in other embodiments. Further details will become apparent with reference to the description and drawings below.

The detailed description described below is provided as an example and is not intended to limit this disclosure to this description. This description will be best understood by referring to the accompanying drawings below.

It is a block diagram of the FOD and defect detection system according to this disclosure. It is a figure which shows the FOD detection of the FOD of the surface and the lower side of a layer using the FOD and defect detection system of this disclosure. FIG. 5 is a diagram showing a laminated cell for forming a wing skin made of carbon fiber according to the first additional embodiment of the present disclosure, wherein the FOD and defect detection system of FIG. 1 is installed in an inspection gantry. .. It is a front view of the inspection gantry of FIG. 2A. It is a front view of the inspection gantry by the 1st modification. It is a front view of the inspection gantry by the 2nd modification. FIG. 5 is a diagram showing an inspection gantry used in a laminated cell forming a carbon fiber spar according to a second additional embodiment of the present disclosure, in which the FOD and defect inspection system of FIG. 1 is installed. FIG. 5 is a diagram showing an inspection gantry used in a laminated cell forming a carbon fiber spar according to a third additional embodiment of the present disclosure, showing a gantry in which the FOD and defect inspection system of FIG. 1 is installed. Is.

In the present disclosure, similar elements are designated by the same reference numerals in all drawings showing various exemplary embodiments of the present disclosure.

US Patent Application No. 14 / 614,198 (“Application No. 198”) is entitled “System and Method for High Speed FOD Detection”, February 4, 2015. The application is filed on the date, transferred to the same transferee as the present application, and includes a plurality of inventors who are the same as the present application. This 198th application, which is incorporated in the present application, describes an infrared excitation source and an FOD detection system using an infrared camera associated therewith. The controller connected to the infrared camera is configured to detect the FOD on the surface of the composite part being manufactured, in which the thermal (infrared) excitation source and this is above the surface of the composite part being manufactured. As the infrared camera associated with (operates in line scan mode) moves, the difference in infrared radiation energy between the composite component and the FOD is determined based on the line threshold of the infrared camera's pixel array. ing.

FOD can also occur below the outer layer (ply) of a composite part being manufactured, but in the system disclosed in Application 198 above, this type of FOD (ie, the lower layer FOD) ) And surface FOD can be difficult to identify. This is because the FOD under the layer needs more time to absorb the energy from the infrared excitation source (this time is the thickness of the upper layer and the infrared energy is transmitted through the upper layer and below it. Based on the time required to reach the FOD in). Because the infrared camera is located at a predetermined distance from the thermal (infrared) excitation source, the layer underneath the layer absorbs enough energy and emits a detectable amount of energy. There is a possibility that the infrared camera will pass above the lower FOD. In view of this, the systems of the present disclosure employ a camera that operates in full two-dimensional mode (rather than line scan mode) at the resolution of the camera (eg, 1024 x 1024 pixels). The camera also includes a controller that analyzes the information generated by the infrared camera to detect underlayer FOD and surface FOD (and other types of defects as described below). It is configured to do so. Detection is based on the difference between the thermal energy emitted from the underlying FOD or some type of surface FOD and the thermal energy emitted from the composite part being manufactured. There are other surface FODs that can be identified based on the reflected infrared energy.

With reference to FIG. 1, a system 100 is shown that detects FOD on the surface of a composite part being manufactured and FOD on the lower side of at least some upper layer in the composite part. System 100 includes yarn threads of composite fibers (a type of foreign matter formed during layup of composite parts), as well as other things that can occur during layup, such as twisting, breaking, poor toe adhesion, wrinkles and bridging. Type of layup anomaly can also be detected. The system 100 includes a thermal (infrared) excitation source 110 and an infrared camera 120 associated with the thermal (infrared) excitation source 110 and located on the member 130 at a predetermined distance. The member 130 may be part of, for example, an overhead inspection gantry in a composite layup machine. The thermal (infrared) excitation source 110 directs a beam of infrared energy 115 toward the workpiece 140 (eg, a composite part being manufactured). The thermal (infrared) excitation source 110 is located at a fixed distance from the work 140, eg, 20 feet above. The infrared camera 120 scans the work 140 as the member 130 moves above the work 140 in the direction indicated by the arrow 150, and outputs information for analysis based on the infrared energy emitted from the work. .. Preferably, the member 130 moves above the work 140 at a constant speed. This speed can be as high as 120 inches / second, but is generally between 50 and 100 inches per second. The controller 170 is connected to activate the thermal (infrared) excitation source 110 (eg, at the start of a scan of the workpiece 140) and to receive information generated by the infrared camera 120. Has been done. The controller 170 is also connected to the user terminal 180 (which may be a simple status indicator) and the layup machine controller 160, and links the operation of the system 100 and the movement of the member 130 with the operation of the layup machine.

In yet another embodiment, the infrared camera 120 may be a radial infrared camera, where the controller 170 provides information provided by the infrared camera 120 while the member 130 moves over the workpiece 140. It may be configured to provide the temperature of the tape (upper layer) and the substrate (inner layer surface) in real time based on the above.

In an alternative embodiment, the position of the member 130 is fixed and the work 140 may be mounted on a movable platform. The infrared camera 120 can scan the entire length of the work 140 as the work 140 moves below the member 130 due to the movement of the platform.

The controller 170 is configured to analyze the information generated by the infrared camera 120 and determine the presence or absence of FOD and other defects on the underside and surface of the layer based on the difference in radiant thermal energy levels. If a lower layer FOD, a surface FOD, or any other type of defect is detected, a message regarding repair response can also be provided via the user terminal 180. Repair measures include, for example, manually removing the surface FOD, marking the position of FOD and other defects under the layer for subsequent repair work, and the like. In one example, as shown in FIG. 1B, the composite part 190 being manufactured includes a surface FOD191, which FOD can be identified based on the difference in infrared energy emitted between the composite part 190 being manufactured and the surface FOD191. be. Further, another composite component 195 being manufactured includes the lower layer FOD 197, and this FOD can be specified by the difference in energy emitted from the boundary peripheral portion of the lower layer FOD 197. In the figure, the peripheral portion of this boundary is shown by the white region 196. In addition, some of the FODs under the layer and the defects under the layer can be identified by the characteristics of the emitted energy being different throughout (not only around the boundary). The controller 170 can also derive other information based on the information from the infrared camera 120, for example, can derive information including real-time measurements of overlap and gaps between the laminated tapes.

Next, referring to FIG. 2A, the lamination cell 200 for performing the production work of the composite part 201 (work) has a layup head 202 mounted on the first movable gantry 203 (that is, a member). Including, the first movable gantry is mounted on the support frame 204. The work 201 has a length and a width, and the gantry 203 is attached to the support frame 204. Since the gantry 203 is attached via a mechanism capable of reciprocating along the length direction of the work 201, the composite material is sequentially laminated from the layup head 202 to the work in the process of manufacturing the composite part during manufacturing. can do. Further, the laminated cell 200 has a second movable gantry 205, and the gantry 205 is also attached to the support frame 204 via a mechanism that enables reciprocating movement along the length direction of the work 201. .. An infrared camera 206 and an associated thermal (infrared) excitation source (not shown in FIG. 2A) are attached to the gantry 205. The infrared camera 206 and the thermal (infrared) excitation source (not shown) of FIG. 2A correspond to the infrared camera 120 and the thermal (infrared) excitation source 110 of FIG. 1A and operate in the same manner. Specifically, a controller (not shown) is connected to the infrared camera 206 and the thermal (infrared) excitation source, and this controller processes information from the infrared camera 206 to form a layer in the work 201. Identify underside or surface FODs or defects.

The infrared camera 206 of FIG. 2A is attached to the member 205 (inspection gantry) at a certain distance upward from the work 201, and at a specific field of view of the infrared camera 206, the work 201 A specific fixed region (a region having a length and a width, the length of which is parallel to the moving direction of the member 205) can be observed. The width of the work 201 may be wider than the range of the angle of view of the infrared camera 206. In such a case, a plurality of cameras and a heat (infrared) excitation source associated with each camera may be mounted on a member moving above the work. For example, as shown in FIG. 2B, three infrared cameras 210, 211, and 212 are attached to the inspection gantry 205, and the entire width of the work to be observed (the width of the work is inspected) is applied to the angle of view of the entire cameras. (Orthogonal to the main direction of movement of the gantry 205) can be inserted. The number of cameras to be installed depends on the width of the workpiece and the angle of view of the cameras, and may be one camera (and the thermal excitation source associated with it), or four or more cameras (and the associated thermal excitation source). , The thermal excitation source associated with each camera).

Alternatively, as shown in FIG. 2C, one infrared camera 216 may be used and the mechanism 217 may allow the camera to move laterally (shown by line 218) along the inspection gantry 215 (FIG. 2C). Although not shown, the thermal (infrared) excitation source associated with the infrared camera 216 also moves laterally along the inspection gantry 215 in conjunction with the camera). In this case, the long band region of the work is imaged by passing over the work, and the passage is performed a plurality of times so that a part of each band region overlaps at the time of the previous passage and the time of the next passage.

Finally, as shown in FIG. 2D, one infrared camera 221 may be attached to the inspection gantry 220 via the pivot 222 (so that it can be moved as shown by line 223). In this case, the inspection gantry 220 may be moved stepwise each time it passes over the work in the longitudinal direction once. A stop period is provided between each of the stepwise movements, and the camera 221 is reciprocally swung to cause the infrared camera 221 to scan the entire width of the work.

The system of FIG. 2A is effective for scanning flat or generally flat workpieces (eg, composite wing skins). However, some of the composite parts formed include a surface that includes a flat top and sides perpendicular to the flat top, instead of having a non-flat surface, such as an aircraft spar. Many have. FIG. 3 shows a system 300 for scanning girders and other non-flat workpieces. Specifically, the system 300 includes an angled inspection gantry 305 (instead of the inspection gantry 205 shown in FIG. 2A). The inspection gantry 305 is equipped with three infrared cameras 310, 320, 330 (not shown in FIG. 3, but as shown in FIG. 1, each camera has an associated heat (not shown). Infrared) attached with excitation source). The infrared camera 310 is attached to the top of the corner of the inspection gantry 305, and the infrared cameras 320 and 330 are attached to the opposite ends of the inspection gantry 305, respectively. In this way, the infrared camera 310 scans the flat top surface of the work (eg, girder), the infrared camera 310 scans one of the side surfaces of the work perpendicular to the flat top surface, and the infrared camera 330 scans the flat top surface. Scan the other side of the workpiece perpendicular to the surface. The system 300 can be inspected only once through a workpiece having a two-dimensional (non-flat) cross section. Some workpieces, such as a spar, have a side surface that is perpendicular to the apex in cross-sectional shape, but some workpieces have a side surface whose angle to the apex is less than 90 degrees. If the system 300 is used, both cases can be dealt with by adjusting the angles at which the cameras 320 and 330 are directed toward the workpiece.

The system 300 shown in FIG. 3 requires three cameras 310, 320, and 330 to inspect a non-flat workpiece in one pass, whereas the system 400 shown in FIG. 4 replaces the cameras 320 and 330. Includes mirrors 420 and 430. The camera 310 is arranged so that the mirrors 420 and 430 are inserted in the angle of view. Further, the angles of the mirrors 420 and 430 are adjusted so that the side surface portion of the non-flat work is within the angle of view of the camera 310. Since the infrared mirrors 420 and 430 are much cheaper than the two infrared cameras that these mirrors 420 and 430 replace, the system 400 can significantly reduce costs compared to the system 300 of FIG. In yet another embodiment, the infrared mirrors 420 and 430 may be convex mirrors. As a result, even if a mirror having a smaller area is used, the entire side surface portion of the non-flat work can be made to fit in the angle of view of the camera 310.

In an alternative embodiment, the system 100 shown in FIG. 1 may be installed on or near the tape layup head (eg, the layup head 202 of the gantry 203 shown in FIG. 2A). This makes it possible to monitor the uncured (green) tape in real time and identify cracks and streaks that occur on the tape prior to adhering the tape to the substrate. Specifically, in the case of a laminated head having low G-forces and an appropriate installation space, an infrared camera is installed on or near the tape laminated head, and an infrared heater installed in the laminated head is used. The temperature of the uncured (green) tape may be raised. As soon as the tape is pulled out of the tape creel, the temperature of the tape rises before it is compressed by the compression rollers. This allows the tape to exhibit sufficient adhesion to the base substrate, i.e., to the top layer composite material laminated in the most recent movement of the tape stacking head. In this embodiment, the infrared camera may be placed directly behind the compression roller to monitor the energy emitted from the tape under the influence of a heater mounted on the head. According to this embodiment, it is not necessary to provide a separate thermal excitation source as in the above-described embodiment.

In addition, the present disclosure also includes embodiments according to the following appendices.

Appendix 1. A member configured to move above the surface and
A thermal excitation source fixed to the member and configured to induce infrared rays on the surface.
An infrared camera fixed to the member at a predetermined distance from the thermal excitation source, scanning the surface as the member moves above the surface, and scanning information about the surface. With an infrared camera configured to detect and output
A controller connected to the thermal excitation source and the infrared camera that processes the scan information from the infrared camera to identify foreign objects or defects located on and / or below the surface. Including the controller,
A system for detecting foreign matter or defects on and / or under the surface.

Appendix 2. A terminal connected to the controller, further including a terminal having a display, further includes a display on the display when the controller further identifies a foreign object or defect located on and / or below the surface. The system according to Appendix 1, which is configured as described above.

Appendix 3. The surface is an outer layer of a composite part formed by the composite layup machine, which is attached to a first gantry for moving above the composite part during formation of the composite part. The system according to any one of Appendix 1 or 2, wherein the member comprises a second gantry for moving separately above the composite part during the formation of the composite part.

Appendix 4. The system according to Appendix 3, wherein the controller is configured to detect defects in the composite component, including twists, breaks, poor adhesion of toes, wrinkles or bridging.

Appendix 5. The system according to any of Appendix 3 or 4, wherein the controller is configured to measure layers and gaps between layers of composite material in real time.

Appendix 6. The surface is an outer layer of a composite part formed by the composite layup machine, which is attached to a first gantry for moving above the composite part during formation of the composite part. The system according to any one of Supplementary note 1 to 5, wherein the member has a head, and the member includes the first gantry.

Appendix 7. The system according to Appendix 6, wherein the infrared camera is a radiation analysis infrared camera.

Appendix 8. The system according to Appendix 7, wherein the controller is configured to provide temperature information for the upper and lower layers of the composite component based on the scan information output from the radioimmunoassay infrared camera.

Appendix 9. The system according to any of Supplementary notes 6 to 8, wherein the controller is configured to detect defects in the composite component, including twists, breaks, poor adhesion of toes, wrinkles or bridging.

Appendix 10. The system according to any of Supplementary note 6 to 9, wherein the controller is configured to measure layers of composite materials and gaps between layers in real time.

Appendix 11. The surface is an outer layer of a composite part formed by a composite material lay-up machine using a carbon fiber reinforced polymer tape, and the carbon fiber reinforced polymer tape is reinforced during operation by contacting with a spool. The polymer tape rubs to form a thread of carbon fiber reinforced polymer that accidentally falls onto the surface, and the controller processes the scan information from the infrared camera to process the carbon fibers on the component surface. The system according to any of Supplementary notes 1 to 10, which is configured to detect a thread of a reinforced polymer.

Appendix 12. With the members fixed above the movable surface,
A thermal excitation source fixed to the member, which induces infrared rays on the surface, and a thermal excitation source.
An infrared camera fixed to the member, which is configured to scan the surface as the surface moves below the member to detect and output scan information about the surface. When,
A controller connected to the thermal excitation source and the infrared camera that processes the scan information from the infrared camera to identify foreign objects or defects located on and / or below the surface. Including the controller,
A system for detecting foreign matter or defects on and / or under the surface.

Appendix 13. A terminal connected to the controller, further including a terminal having a display, further includes a display on the display when the controller further identifies a foreign object or defect located on and / or below the surface. 12. The system according to Appendix 12.

Appendix 14. The surface is an outer layer of a composite part formed by a composite layup machine, the composite layup machine has a head attached to a gantry, and the composite part is forming the composite part. The system according to any of Appendix 12 or 13, wherein the member moves below the gantry and comprises the gantry.

Appendix 15. The infrared camera is a radiation analysis infrared camera, and the controller is configured to provide upper layer and subsurface temperature information in the composite component based on information output from the radiation analysis infrared camera. The system according to Appendix 14.

Appendix 16. The system according to any of Supplementary note 12-15, wherein the controller is configured to detect defects in the composite component, including twists, breaks, poor adhesion of toes, wrinkles or bridging.

Appendix 17. The system according to any of Supplementary note 12-16, wherein the controller is configured to measure layer-to-layer overlap and gaps of a composite material in real time.

Appendix 18. The surface is an outer layer of a composite part formed by a composite material lay-up machine using a carbon fiber reinforced polymer tape, and the carbon fiber reinforced polymer tape is reinforced during operation by contacting with a spool. The polymer tape rubs to form a thread of carbon fiber reinforced polymer that accidentally falls onto the surface, and the controller processes the scan information from the infrared camera to reinforce the carbon fibers on the surface. The system according to any of Appendix 12-17, which is configured to detect polymer threads.

Appendix 19. A step of guiding an infrared beam from an infrared excitation source to the surface of the work,
A step of scanning the surface of the work with an infrared camera to detect and output scan information about the surface of the work.
A step of processing the scan information from the infrared camera to identify foreign objects or defects located on and / or below the surface of the work.
A method for detecting foreign matter or defects on and / or under the surface of a workpiece.

Appendix 20. The infrared camera is a radiation analysis infrared camera, and further
19. The method of Appendix 19, comprising processing the scan information from the infrared camera to provide temperature information for the upper and lower layers of the work.

Although the present disclosure has been specifically illustrated and described using preferred embodiments and various aspects thereof, it will be appreciated by those skilled in the art that various modifications and modifications can be made without departing from the spirit and scope of the present disclosure. Will be clear. The appended claims should be construed to include the embodiments described herein, the modifications described above, and their equivalents.

Claims (6)

A member configured to move above the surface and
A thermal excitation source fixed to the member and configured to induce infrared rays on the surface.
An infrared camera fixed to the member at a predetermined distance from the thermal excitation source, scanning the surface as the member moves above the surface, and scanning information about the surface. With an infrared camera configured to detect and output
A controller connected to the thermal excitation source and the infrared camera that processes the scan information from the infrared camera to identify foreign objects or defects located on and / or below the surface. With the controller
A terminal connected to the controller, including a terminal having a display.
The controller is further configured to display on the display when it identifies a foreign object or defect located on and / or below the surface.
The surface is an outer layer of a composite part formed by the composite layup machine, which is attached to a first gantry for moving above the composite part during formation of the composite part. The member comprises a second gantry for moving separately above it during the formation of the composite part.
A system for detecting foreign matter or defects on and / or under the surface. The system of claim 1, wherein the controller is configured to detect defects in the composite component, including twists, breaks, poor toe adhesion, wrinkles or bridging. The system according to claim 1 or 2, wherein the controller is configured to measure layers and gaps between layers of composite material in real time. The system according to any one of claims 1 to 3, wherein the infrared camera is a radiation analysis infrared camera. The system according to claim 4, wherein the controller is configured to provide temperature information for the upper layer and the lower surface of the composite component based on the scan information output from the radiation analysis infrared camera. The surface is an outer layer of a composite part formed by a composite material lay-up machine using a carbon fiber reinforced polymer tape, and the carbon fiber reinforced polymer tape is reinforced during operation by contacting with a spool. polymeric tapes rubbing, to form a yarn Mari carbon fiber reinforced polymer which accidentally fall to the surface, said controller processing said scan information from the infrared camera, in front Symbol table surfaces on carbon The system according to any one of claims 1 to 5, which is configured to detect a thread of a fiber-reinforced polymer.

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